Formation Method of Satellite Distributed Payload

A distributed and satellite technology, applied in the field of satellite distributed load formation, can solve the problem of low control accuracy

Active Publication Date: 2019-06-21
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

[0005] In order to overcome the deficiency of low control precision of existing satellite autonomous formation flight control methods, the present invention provides a formation method of satellite distributed load

Method used

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  • Formation Method of Satellite Distributed Payload
  • Formation Method of Satellite Distributed Payload
  • Formation Method of Satellite Distributed Payload

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Embodiment Construction

[0065] refer to Figure 1-5 . The specific steps of the formation method of satellite distributed load of the present invention are as follows:

[0066] Step 1. Determine the position and connection method of each component on the satellite.

[0067]Design the split Stewart drive platform4. The separated Stewart driving platform 4 uses the two oblique interfaces of the cube as the upper and lower platforms, and the six edges of the cube serve as the six legs of the separated Stewart driving platform 4 . Six separate electromagnetic voice coil actuators 2 are used instead of telescopic actuators to control the six-degree-of-freedom motion of distributed loads. Assuming that there are three distributed loads on the satellite, namely the distributed main load 1, the first distributed slave load 3 and the second distributed slave load 6, determine the position of each distributed load on the satellite, separate Stewart drive The platform 4 connects the satellite body 5 with th...

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Abstract

The invention discloses a satellite distributed load formation method, which is used to solve the technical problem of low control precision of the existing satellite autonomous formation flight control method. The technical solution is to arrange distributed loads at different positions of the same satellite according to different mission requirements. The load formation consists of a main load and several slave loads. All loads in the formation work together to complete a given task. A separate Stewart drive platform is used to connect the satellite body to the load, and a separate electromagnetic voice coil actuator replaces the retractable outrigger as the actuator, and the proportional-derivative (PD) control law is used to control the formation of distributed loads. This method meets the requirements of high precision, high stability, and ultrastatic environment proposed by large-aperture optical application systems such as distributed optical imaging, and can complete a variety of space tasks; at the same time, the actuator does not consume working fluid and does not cause micro-vibration. And there is no need to unload, which effectively improves the control accuracy of the satellite load.

Description

technical field [0001] The invention relates to a satellite autonomous formation flight control method, in particular to a satellite distributed load formation method. Background technique [0002] The satellite load formation technology is an emerging technology different from the traditional satellite formation. It refers to arranging distributed loads at different positions on the same satellite, and forming these loads to maintain high-precision relative to a certain main load. position and relative posture to jointly accomplish certain tasks. Distributed optical imaging and other large-aperture optical application systems have put forward requirements for satellite payload formation technology such as high precision, high stability, and hyperstatic environment. [0003] The traditional satellite formation technology, that is, formation of different satellites, generally uses the linearized C-W equation to describe the relative motion between two satellites; when perfor...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/22B64G1/24
CPCB64G1/22B64G1/24B64G1/245
Inventor 刘磊熊敏魏震唐硕
Owner NORTHWESTERN POLYTECHNICAL UNIV
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